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WO2006085054A1 - Protection de surfaces aérodynamiques contre la glace - Google Patents

Protection de surfaces aérodynamiques contre la glace Download PDF

Info

Publication number
WO2006085054A1
WO2006085054A1 PCT/GB2006/000374 GB2006000374W WO2006085054A1 WO 2006085054 A1 WO2006085054 A1 WO 2006085054A1 GB 2006000374 W GB2006000374 W GB 2006000374W WO 2006085054 A1 WO2006085054 A1 WO 2006085054A1
Authority
WO
WIPO (PCT)
Prior art keywords
tracks
structure according
heater
ink
substrate
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/GB2006/000374
Other languages
English (en)
Inventor
Greg Peter Wade Fixter
Christopher John Gilmore
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Qinetiq Ltd
Original Assignee
Qinetiq Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from GB0502644A external-priority patent/GB0502644D0/en
Priority claimed from GB0515078A external-priority patent/GB0515078D0/en
Application filed by Qinetiq Ltd filed Critical Qinetiq Ltd
Priority to DE602006006547T priority Critical patent/DE602006006547D1/de
Priority to US11/883,102 priority patent/US9771158B2/en
Priority to DK06709622T priority patent/DK1846293T3/da
Priority to EP06709622A priority patent/EP1846293B1/fr
Priority to AT06709622T priority patent/ATE430091T1/de
Publication of WO2006085054A1 publication Critical patent/WO2006085054A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • B64D15/14—De-icing or preventing icing on exterior surfaces of aircraft by electric heating controlled cyclically along length of surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
    • F03D80/40—Ice detection; De-icing means
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Definitions

  • the present invention relates to the ice protection of aerodynamic surfaces.
  • the invention may be applicable to the protection of any form of aerodynamic surface which is liable to encounter icing conditions in service, including in particular the surfaces of aircraft wings, propellers, stabilisers, fins, engine nacelles and radomes, helicopter rotor blades and wind energy turbine blades.
  • ice accretion can occur on an aerodynamic surface when subject to an airflow containing airborne water at a temperature below or near its freezing point.
  • the uncontrolled build up of ice on such surfaces is undesirable for many reasons, including the additional weight which must be carried, reduction of the aerodynamic efficiency of the surface, the imposition of out of balance loads on the structure, and the danger to other structures or persons from uncontrolled shedding of the ice.
  • Many forms of ice protection systems for such surfaces are therefore already known, one large class of which comprises electrothermal means where electrical resistance heating elements, for example in the form of wires, foils, sprayed metal matrices or conductive fabrics, are used to raise or maintain the temperature of the surface above the local freezing point.
  • anti-icing refers to the process of maintaining a surface at a temperature above freezing point over a continuous period of time so that ice is prevented from forming
  • de-icing refers to the process of permitting a certain limited amount of ice to build up on a surface and periodically removing it by heating the surface at selected intervals.
  • the present invention seeks to provide a form of electrothermal ice protection system which is adaptable to use with a wide variety of aerodynamic surfaces and may offer significant manufacturing cost advantages in comparison with systems currently in service.
  • the invention accordingly resides in a structure including an aerodynamic surface and equipped with an electrothermal heater mat in proximity to such surface for ice protection of the same, said mat comprising a substrate bearing heater tracks of a material of selected resistivity, said tracks being formed by printing onto the substrate with a thermosetting ink containing electrically conductive particles and curing such ink.
  • the invention also resides perse in a heater mat as defined above in the first-mentioned aspect, and in a method of producing the same by printing heater tracks of a material of selected resistivity onto a substrate with a thermosetting ink containing electrically conductive particles and curing such ink.
  • an electrical current is caused to pass through the printed tracks to cause Joulean heating, and the supply of electrical energy will be controlled to provide anti-icing or de-icing of the respective surface, or a combination of the two over different regions, as required.
  • the liberation of heat for this purpose is of course a function of the current (and therefore the applied voltage) and the resistivity of the material in the respective tracks, the latter being dependent on the composition of the ink and the width and thickness at which it is printed, all of which can be controlled to achieve a desired performance.
  • heaters of practically any desired configuration to suit respective surfaces to be protected can be produced relatively inexpensively, and with accurate control of the shape and thickness of the resistive tracks.
  • the ink system which is used for producing the resistive tracks preferably comprises a thermosetting medium - such as a phenolic (phenol/formaldehyde) or epoxy resin - loaded with carbon particles and optional inert filler (e.g. alumina) to achieve a desired resistivity.
  • a thermosetting medium - such as a phenolic (phenol/formaldehyde) or epoxy resin - loaded with carbon particles and optional inert filler (e.g. alumina) to achieve a desired resistivity.
  • a thermosetting medium - such as a phenolic (phenol/formaldehyde) or epoxy resin - loaded with carbon particles and optional inert filler (e.g. alumina) to achieve a desired resistivity.
  • Such inks can produce heater tracks with accurately determined and stable resistances when printed and cured under controlled conditions, and have been found to be suitable for screen printing tracks with surface resistivities from 10 to 100,000 Ohm/square depending on the ratio of carbon to inert filler,
  • thermosetting inks can be printed in a single thick (in printing terms) film, typically up to around 25 ⁇ m but selectable by appropriate choice the mesh type of the screen.
  • Phenolic based inks are typically cured at 180 0 C for an hour. Some epoxy based inks may cure at normal room temperatures, although are more usually cured at elevated temperature to speed the setting reaction.
  • bus bars or the like conductors for the supply of electrical energy to the resistive tracks are also printed on the same substrate, in this case typically with an ink loaded with particles of silver or copper.
  • thermosetting thick film inks comprising a phenolic or epoxy resin loaded with silver have been used to print conductors with a surface resistivity in the region of 0.05 Ohm/square.
  • an alternative ink system comprises a highly loaded paste of silver particles in a high boiling point solvent which, when printed and then fired at high temperature (typically 200 0 C for half an hour) converts to virtually pure metal and has been found to produce deposits with a surface resistivity in the region of 0.005 Ohm/square.
  • the substrate in a mat according to the invention may be rigid or flexible, although a flexible substrate has the advantage of enabling ready conformance of the mat to profiled surfaces during assembly and accommodating any natural flexure of the structure in service.
  • a thin polyimide or other heat-resistant polymer sheet is a preferred flexible substrate.
  • this may be achieved by an additional printing step to deposit an electrically insulative material over the tracks/conductors or simply over the whole surface of the mat.
  • This layer may comprise a varnish composed of the same resin as is used in the type of thermosetting ink referred to above (when the latter is chosen for printing the resistive tracks and/or conductors) but without the carbon and/or metal inclusions.
  • This may be of advantage in providing an insulating layer with similar mechanical or other (non-electrical) properties to the tracks/conductors.
  • other materials may be used for this purpose, in particular UV curable systems which may be quicker to cure and more flexible.
  • an additional insulative layer of this kind may provide a base for further printed heater tracks and/or associated conductors. Gaps can be left in the insulative layer if connections are required to the tracks/conductors beneath.
  • This kind of sandwich construction enables more complex designs of heater networks and positioning of bus bars (which are essentially cold spots) to be achieved than with a single printed layer.
  • a similar effect could be achieved by printing on both sides of the basic substrate. For example heater tracks could be printed on one side overlapping bus bars printed on the other side, to minimise the cold spot effect, with electrical connections being made through the substrate as required.
  • the resistive tracks could be printed onto a reinforcement cloth to be incorporated in a polymer composite material forming part of the aerodynamic structure, the tracks becoming encapsulated within the composite for enhanced physical protection.
  • Figure 1 is a vertical section, not to scale, through part of the structure of a helicopter rotor blade equipped with an ice protection heater mat in accordance with the invention
  • Figure 2 is a plan view, prior to installation, of one embodiment of heater mat for the structure of Figure 1 ;
  • Figure 3 illustrates the configuration of the heater mat of Figure 1 when installed.
  • this illustrates part of the upper portion of a helicopter rotor blade structure close to its leading edge.
  • Indicated at 1 and 2 are parts of the internal base layers of the blade construction and indicated at 3 is part of the usual erosion shield (metallic or polymer) which defines the outer surface of the leading edge region.
  • an electrothermal heater mat 4 comprising printed resistive tracks (not shown in Figure 1 ) for heating the erosion shield for anti-icing and/or de-icing purposes when energised, this being shown sandwiched between layers of adhesive 5 which provide electrical insulation and bonding of the erosion shield to the base structure.
  • FIGs 2 and 3 One embodiment of a heater mat 4 is shown in Figures 2 and 3, it being understood that this is one of a plurality of such mats which will be installed in spanwise succession along the length of the blade. It is shown in flat form in Figure 2 and in Figure 3 in the curved form which it adopts when installed beneath the erosion shield around the leading edge region of the blade. The relative position of the spanwise extreme leading edge is shown by the broken line LE in Figure 2.
  • the tracks 7A-7E are printed in a single layer with a carbon-loaded thermosetting ink so as to be electrically conductive but with high resistance so as to generate heat for transfer to the erosion shield when energised.
  • a common bus bar 8 is provided in contact with one end of each track 7A-7E and individual terminals 9A-9E are provided in contact with the respective opposite ends of each track, the bus bar and terminals being connected to an electrical supply system (not shown) so that if required the energisation of each track can be controlled individually.
  • the bus bar 8 and terminals 9A-9E are also formed by screen printing a conductive ink onto the substrate 6, in this case loaded with silver or copper for higher conductivity.
  • the heater mat 4 is flexed to lie under the erosion shield with the central track 7C disposed to coincide with the extreme leading edge, tracks 7B and 7A extending aft beneath the upper surface of the erosion shield and tracks 7D and 7E extending aft beneath its lower surface.
  • the energisation of each track can be controlled individually and in one embodiment the following control protocol may be adopted. That is to say, during flight through icing conditions the central track 7C is energised continuously so that the region of the erosion shield around the extreme leading edge is maintained above freezing point continuously, this being the region of maximum impact with water droplets during flight.
  • the tracks 7B, 7A, 7D and 7E are not energised continuously but are used for "runback" de-icing. That is to say water running back from the anti-iced leading edge region forms frozen rivulets over the upper and lower surfaces of the erosion shield which are removed periodically by energising the tracks 7B, 7A and 7D, 7E to heat the corresponding regions of the erosion shield in a cyclic manner.
  • the "on" times of the upper and lower heating tracks may alternate, thus limiting the total power requirement for the mat at any time.
  • the upper and lower tracks may be cycled individually to meet the de-icing requirement of any particular blade design or operating conditions.
  • the illustrated mat 4 will be one of a plurality of such mats installed in succession across the span of the blade.
  • the illustrated embodiment is of rectangular planform so that the adjacent edges of successive mats extend in the chordwise direction.
  • continuous chordwise ice "bridges" may form around the erosion shield on the regions above the gaps between the ends of the tracks in adjacent mats which may receive insufficient heat flow to shed this ice.
  • the mats may instead be configured to present edges which are oblique to the chord of the blade so that the ends of the tracks are staggered in the chordwise direction and run back water from any spanwise location will always encounter at least one fully heatable region.
  • heater mats may be provided where the resistive tracks extend in a generally chordwise rather than spanwise direction, and again may be at an oblique angle to the chord.
  • the tracks 7A-7E are shown printed on the side of the substrate 6 which faces the erosion shield in use. It may alternatively be preferred to orient the mat with its heating tracks facing inward away from the erosion shield, which would facilitate repair or replacement of the shield without damaging the tracks.
  • the thermal inertia of a thin polyimide substrate as exemplified above should be sufficiently low to permit this orientation without compromising the ice protection performance of the mat.
  • tracks 7A-7E are shown as rectilinear elements in Figures 2 and 3 they may instead be configured with a serpentine (wavy) or other non-linear form for the purpose of stress relief within the blade.
  • heater mats of the same basic design as described above with reference to Figures 2 and 3 can similarly be installed around the leading edges of the wings, stabilisers and fins of fixed-wing aircraft.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Sustainable Development (AREA)
  • Surface Heating Bodies (AREA)
  • Apparatuses And Processes For Manufacturing Resistors (AREA)
  • Thermistors And Varistors (AREA)
  • Resistance Heating (AREA)

Abstract

L’invention concerne un tapis à radiateur électrothermique pour empêcher le givre ou dégivrer une pale de rotor d’hélicoptère ou autre surface aérodynamique, comprenant un substrat, comme une feuille de polyimide flexible 6, des chemins de roulement 7A-7E d’un matériau de résistivité électrique sélectionnée, ces chemins étant formés par impression sur le substrat avec une encre thermodurcissable chargée de particules électriquement conductrices (par exemple carbone). Les jeux de barres et bornes électriques 8/9A-9E peuvent également être imprimés pour injecter de l’électricité aux chemins résistifs, à l’aide d’une encre chargée de particules d’un matériau de conductivité supérieure comme le cuivre ou l’argent.
PCT/GB2006/000374 2005-02-09 2006-02-03 Protection de surfaces aérodynamiques contre la glace Ceased WO2006085054A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE602006006547T DE602006006547D1 (de) 2005-02-09 2006-02-03 Elektrothermische heizvorrichtung zum schutz von aerodynamischen oberflächen vor eis und ihre herstellungsverfahren
US11/883,102 US9771158B2 (en) 2005-02-09 2006-02-03 Ice protection of aerodynamic surfaces
DK06709622T DK1846293T3 (da) 2005-02-09 2006-02-03 Elektrotermisk varmer til isbeskyttelse af aerodynamiske overflader og fremgangsmåde til at producere den
EP06709622A EP1846293B1 (fr) 2005-02-09 2006-02-03 Dispositif de chauffage électrothermique pour la protection de surfaces aérodynamiques contre la glace et son procédé de fabrication
AT06709622T ATE430091T1 (de) 2005-02-09 2006-02-03 Elektrothermische heizvorrichtung zum schutz von aerodynamischen oberflächen vor eis und ihre herstellungsverfahren

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB0502644.8 2005-02-09
GB0502644A GB0502644D0 (en) 2005-02-09 2005-02-09 Ice protection of aerodynamic surfaces
GB0515078.4 2005-07-22
GB0515078A GB0515078D0 (en) 2005-07-22 2005-07-22 Ice protection of aerodynamic surfaces

Publications (1)

Publication Number Publication Date
WO2006085054A1 true WO2006085054A1 (fr) 2006-08-17

Family

ID=36021795

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2006/000374 Ceased WO2006085054A1 (fr) 2005-02-09 2006-02-03 Protection de surfaces aérodynamiques contre la glace

Country Status (6)

Country Link
US (1) US9771158B2 (fr)
EP (1) EP1846293B1 (fr)
AT (1) ATE430091T1 (fr)
DE (1) DE602006006547D1 (fr)
DK (1) DK1846293T3 (fr)
WO (1) WO2006085054A1 (fr)

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WO2009023424A3 (fr) * 2007-08-10 2009-05-22 3M Innovative Properties Co Films résistants à l'érosion utilisables sur des surfaces aérodynamiques portées à haute température
WO2010026364A1 (fr) * 2008-09-08 2010-03-11 Qinetiq Limited Appareil à émission thermique
EP2196393A1 (fr) * 2008-12-11 2010-06-16 Hutchinson Système d'antigivrage/ dégivrage, son procédé de fabrication et structure d'aéronef l'incorporant.
WO2011087412A1 (fr) * 2010-01-14 2011-07-21 Saab Ab Système de dégivrage/antigivrage multifonctionnel
WO2011096851A1 (fr) * 2010-01-14 2011-08-11 Saab Ab Système de dégivrage/antigivrage multifonctionnel pour éolienne
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WO2016012719A1 (fr) * 2014-07-22 2016-01-28 Aircelle Procédé de mise en place d'un système de dégivrage sur un aéronef, comportant le dépôt de couches de matériaux à l'état solide et/ou fluide
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WO2018113875A1 (fr) * 2016-12-20 2018-06-28 Vestas Wind Systems A/S Procédés et systèmes pour réparer des pales d'éolienne
EP3015707B1 (fr) 2014-10-31 2018-07-04 Senvion GmbH Éolienne et procédé de dégivrage d'une éolienne
EP3530936A1 (fr) * 2018-02-27 2019-08-28 Beijing Goldwind Science & Creation Windpower Equipment Co. Ltd. Appareil de chauffage électrique pour le dégivrage, son procédé de fabrication, pale et éolienne la comportant
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CA2770950A1 (fr) * 2009-08-11 2011-02-17 EcoTemp International, Inc. Film de degivrage pour profil aerodynamique de turbine eolienne
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EP2884818B1 (fr) * 2012-08-08 2023-06-07 CENTITVC - Centro de Nanotecnologia e Materiais Tecnicos, Funcionais e Inteligentes Dispositif de chauffage, procédés d'impression respectifs et utilisation
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US20180370637A1 (en) * 2017-06-22 2018-12-27 Goodrich Corporation Electrothermal ice protection systems with carbon additive loaded thermoplastic heating elements
US11965487B2 (en) 2017-06-30 2024-04-23 Vestas Wind Systems A/S Electro-thermal heating elements
US10960983B2 (en) * 2017-09-01 2021-03-30 Textron Innovations Inc. Tailored rotor-blade ice-protection system
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US11084593B2 (en) * 2018-10-11 2021-08-10 Goodrich Corporation Additive manufactured heater elements for propeller ice protection
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DK4027010T3 (da) * 2021-01-12 2023-11-20 Siemens Gamesa Renewable Energy Innovation & Technology SL Vinge til en vindmølle og fremgangsmåde til fremstilling af en vinge
CN113086156B (zh) * 2021-04-08 2022-05-17 南京航空航天大学 一种具有除冰功能的翼型前缘及翼型前缘的制备方法
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FR3144110B1 (fr) * 2022-12-23 2025-04-11 Safran Aerosystems Systeme de dégivrage d’une piece, notamment une pale d’aeronef, avec protection a l’abrasion integree

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EP2641948A1 (fr) * 2007-08-10 2013-09-25 3M Innovative Properties Company Films résistants à l'érosion utilisables sur des surfaces aérodynamiques portées à haute température
CN101778916B (zh) * 2007-08-10 2015-09-23 3M创新有限公司 用于受热气动力面上的防腐薄膜
CN101778916A (zh) * 2007-08-10 2010-07-14 3M创新有限公司 用于受热气动力面上的防腐薄膜
JP2010535668A (ja) * 2007-08-10 2010-11-25 スリーエム イノベイティブ プロパティズ カンパニー 加熱空気力学的表面上で使用するための耐浸食性フィルム
US10272985B2 (en) 2007-08-10 2019-04-30 3M Innovative Properties Company Erosion resistant films for use on heated aerodynamic surfaces
WO2009023424A3 (fr) * 2007-08-10 2009-05-22 3M Innovative Properties Co Films résistants à l'érosion utilisables sur des surfaces aérodynamiques portées à haute température
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WO2010026364A1 (fr) * 2008-09-08 2010-03-11 Qinetiq Limited Appareil à émission thermique
FR2939767A1 (fr) * 2008-12-11 2010-06-18 Hutchinson Systeme d'antigivrage/degivrage, son procede de fabrication et structure d'aeronef l'incorporant
EP2196393A1 (fr) * 2008-12-11 2010-06-16 Hutchinson Système d'antigivrage/ dégivrage, son procédé de fabrication et structure d'aéronef l'incorporant.
WO2011096851A1 (fr) * 2010-01-14 2011-08-11 Saab Ab Système de dégivrage/antigivrage multifonctionnel pour éolienne
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WO2011087412A1 (fr) * 2010-01-14 2011-07-21 Saab Ab Système de dégivrage/antigivrage multifonctionnel
CN102811906A (zh) * 2010-01-14 2012-12-05 萨博公司 风轮机的多功能除冰/防结冰系统
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CN104395193A (zh) * 2012-06-25 2015-03-04 埃尔塞乐公司 用于除霜设备的电加热组件
FR3024124A1 (fr) * 2014-07-22 2016-01-29 Aircelle Sa Procede de mise en place d’un systeme de degivrage sur un aeronef, comportant le depot de couches de materiaux a l’etat solide et/ou fluide
WO2016012719A1 (fr) * 2014-07-22 2016-01-28 Aircelle Procédé de mise en place d'un système de dégivrage sur un aéronef, comportant le dépôt de couches de matériaux à l'état solide et/ou fluide
EP3015707B1 (fr) 2014-10-31 2018-07-04 Senvion GmbH Éolienne et procédé de dégivrage d'une éolienne
FR3060529A1 (fr) * 2016-12-16 2018-06-22 Dassault Aviation Piece d'aeronef munie d'un revetement chauffant destinee a entrer en contact avec une masse d'air situee autour de l'aeronef, aeronef et procede associes
WO2018113875A1 (fr) * 2016-12-20 2018-06-28 Vestas Wind Systems A/S Procédés et systèmes pour réparer des pales d'éolienne
US11118573B2 (en) 2016-12-20 2021-09-14 Vestas Wind Systems A/S Methods and systems for repairing wind turbine blades
EP3530936A1 (fr) * 2018-02-27 2019-08-28 Beijing Goldwind Science & Creation Windpower Equipment Co. Ltd. Appareil de chauffage électrique pour le dégivrage, son procédé de fabrication, pale et éolienne la comportant
US11598316B2 (en) 2018-02-27 2023-03-07 Beijing Goldwind Science & Creation Windpower Equipment Co., Ltd. Electric heating apparatus for deicing, method for manufacturing the same, blade and wind turbine including the same
US11242151B2 (en) 2018-10-16 2022-02-08 Goodrich Corporation Method of using printed highly flexible conductive ink bus bars to transfer power to heated components

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DK1846293T3 (da) 2009-08-10
DE602006006547D1 (de) 2009-06-10
EP1846293A1 (fr) 2007-10-24
ATE430091T1 (de) 2009-05-15
US9771158B2 (en) 2017-09-26
US20080099617A1 (en) 2008-05-01

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